81738 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Rules and Regulations 

procedures in 7 CFR part 3550, as 

appropriate. 

* * * * * 

[FR Doc. 2015–33038 Filed 12–30–15; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF AGRICULTURE 

National Institute of Food and 

Agriculture 

7 CFR Part 3400 

Special Research Grants Program 

CFR Correction 

In Title 7 of the Code of Federal 

Regulations, Part 2000 to End, revised as 

of January 1, 2015, on page 209, in 

§ 3400.4, in paragraph (c)(14), remove 

the term ‘‘engaged by Director’’ and add 

the term ‘‘engaged by the Director’’ in its 

place. 

[FR Doc. 2015–33039 Filed 12–30–15; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF AGRICULTURE 

National Institute of Food and 

Agriculture 

7 CFR Part 3415 

Biotechnology Risk Assessment 

Research Grants Program 

CFR Correction 

In Title 7 of the Code of Federal 

Regulations, Part 2000 to End, revised as 

of January 1, 2015, on page 307, in 

§ 3415.5, in paragraph (a), remove the 

term ‘‘upon which the Administrator’’ 

and add in its place the term ‘‘upon 

which the Director or Administrator’’. 

[FR Doc. 2015–33041 Filed 12–30–15; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF AGRICULTURE 

Rural Housing Service 

7 CFR Part 3550 

Direct Single Family Housing Loans 

and Grants 

CFR Correction 

In Title 7 of the Code of Federal 

Regulations, Part 2000 to End, revised as 

of January 1, 2015, on page 406, in 

§ 3550.150, remove the third sentence. 

[FR Doc. 2015–33043 Filed 12–30–15; 8:45 am] 

BILLING CODE 1505–01–D 

FEDERAL DEPOSIT INSURANCE 

CORPORATION 

12 CFR Part 325 

Capital Maintenance 

CFR Correction 

In Title 12 of the Code of Federal 

Regulations, Parts 300 to 499, revised as 

of January 1, 2015, on page 406, in 

§ 325.203, in paragraph (b)(3), the 

following phrase is added to the last 

sentence: ‘‘nonmember bank or state 

savings association becomes a covered 

bank.’’ 

[FR Doc. 2015–33048 Filed 12–30–15; 8:45 am] 

BILLING CODE 1505–01–D 

NATIONAL CREDIT UNION 

ADMINISTRATION 

12 CFR Part 745 

Share Insurance and Appendix 

CFR Correction 

In Title 12 of the Code of Federal 

Regulations, Parts 600 to 899, revised as 

of January 1, 2015, on page 876, in 

subpart B, remove § 745.14. 

[FR Doc. 2015–33056 Filed 12–30–15; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0683; Directorate 

Identifier 2014–NM–196–AD; Amendment 

39–18355; AD 2015–26–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 767–200, –300, 

and –300F series airplanes. This AD was 

prompted by a finding that certain 

barrel nuts installed at the vertical fin 

may be subject to stress corrosion and 

cracking. This AD requires either 

repetitive inspections of vertical fin 

barrel nuts for corrosion or a magnetic 

check to identify certain barrel nuts, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

corroded and loose barrel nuts that 

attach the vertical fin to body section 

48; this condition could result in 

reduced structural integrity of the 

vertical fin attachment joint, loss of the 

vertical fin, and consequent loss of 

controllability of the airplane. 

DATES: This AD is effective February 4, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 4, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0683; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6447; 

fax: 425–917–6590; email: 

wayne.lockett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

767–200, –300, and –300F series 

airplanes. The NPRM published in the 

Federal Register on April 10, 2015 (80 

FR 19248). The NPRM was prompted by 

a finding that certain barrel nuts 

installed at the vertical fin may be 

subject to stress corrosion and cracking. 

The NPRM proposed to require either 


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Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Rules and Regulations 81739 

repetitive inspections of vertical fin 

barrel nuts for corrosion or a magnetic 

check to identify certain barrel nuts, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

corroded and loose barrel nuts that 

attach the vertical fin to body section 

48; this condition could result in 

reduced structural integrity of the 

vertical fin attachment joint, loss of the 

vertical fin, and consequent loss of 

controllability of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 19248, 

April 10, 2015) and the FAA’s response 

to each comment. 

Request To Revise Applicability 

Boeing and Air New Zealand 

requested that additional clarification be 

added to paragraph (c) of the proposed 

AD (80 FR 19248, April 10, 2015). 

Boeing stated that this addition will add 

clarity because there is an existing AD 

(AD 2003–10–11, Amendment 39–13156 

(68 FR 28703, May 27, 2003)) of a 

similar subject that covers only Boeing 

Model 767 airplanes, line numbers 1 

through 574 inclusive. Boeing requested 

we clarify that Boeing Alert Service 

Bulletin 767–53A0261, dated August 12, 

2014, addresses only Boeing Model 767 

airplanes with line numbers 575 

through 681 inclusive. Air New Zealand 

asked whether the NPRM would 

supersede AD 2003–10–11. 

We agree to provide clarification. 

Only Model 767 airplanes with line 

numbers 575 through 681 inclusive are 

affected by this AD. Some proposed 

requirements overlap with the 

requirements of AD 2003–10–11, 

Amendment 39–13156 (68 FR 28703, 

May 27, 2003). We have therefore 

revised the applicability of this AD to 

specify airplanes identified in Boeing 

Alert Service Bulletin 767–53A0261, 

dated August 12, 2014, which limits the 

applicability to line numbers 575 

through 681 inclusive. 

Request To Add Clarification About the 

Previous Replacement of Discovered H– 

11 Barrel Nuts With Inconel 

Alternatives 

Boeing stated that operators may have 

already replaced discovered H–11 barrel 

nuts with Inconel alternatives. Boeing 

requested that we revise the NPRM (80 

FR 19248, April 10, 2015) to specify the 

‘‘Compliance Time Exceptions’’ noted 

in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 767– 

53A0261, dated August 12, 2014. Those 

‘‘exceptions’’ would specify that no 

further action is required at the vertical 

stabilizer attachment point, provided 

the following conditions are met: 

• The vertical stabilizer attachment 

barrel nut has been inspected; 

• No H–11 steel barrel nut was found 

during the inspection; and 

• Any replacement barrel nut is either 

a drawing configuration barrel nut made 

from an alternative material to H–11 

steel; or a barrel nut made from 

alternative material to H–11 steel 

approved by the FAA or by a Boeing 

Company Authorized Representative. 

We do not agree with the request 

because paragraph (g) of this AD already 

makes reference to paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 767–53A0261, dated August 12, 

2014, which lists the compliance time 

exceptions. We have not changed this 

AD regarding this issue. 

Request To Clarify Terminating Action 

for Repetitive Inspections and 

Replacement 

United Parcel Service (UPS) requested 

that we provide terminating action 

similar to that provided in paragraph (i) 

of AD 2013–18–02, Amendment 39– 

17575 (78 FR 57049, September 17, 

2013). 

We agree with the commenter’s 

request. The NPRM (80 FR 19248, April 

10, 2015) is not clear whether the 

repetitive inspections are terminated by 

replacement with an Inconel barrel nut 

or by a finding of no H–11 steel barrel 

nut installed. Replacing a barrel nut at 

an attachment point location with a new 

Inconel barrel nut in accordance with 

Part 5 of Boeing Alert Service Bulletin 

767–53A0261, dated August 12, 2014, 

terminates the inspections and 

replacement required by paragraph (g) 

of this AD for that attachment point 

location only. In addition, if no H–11 

steel barrel nut is found installed at an 

attachment point location, the repetitive 

inspections and replacement required 

by paragraph (g) of this AD are 

terminated for that attachment location 

only. We have added a new paragraph 

(h) to this AD to clarify the terminating 

action and redesignated the subsequent 

paragraphs accordingly. 

Request For Clarification of Barrel Nuts 

To Be Replaced 

UPS requested that we provide 

clarification of paragraph (g)(1)(ii)(B) of 

the proposed AD (80 FR 19248, April 

10, 2015). UPS stated that its 

interpretation of paragraph (g)(1)(ii)(B) 

of the proposed AD is that replacement 

of only H–11 steel barrel nuts is 

required, although it appears that all 

barrel nuts are to be replaced, even if 

the installed barrel nuts are Inconel or 

other approved barrel nuts. 

We agree that clarification is 

necessary. Operators are required to do 

all actions specified in either paragraph 

(g)(1) or (g)(2) of this AD. Paragraph 

(g)(1) of this AD is only an internal and 

external detailed inspection of the barrel 

nuts and does not provide a method for 

determination of the material of the 

barrel nuts. Paragraph (g)(2) of this AD 

provides the method to determine if the 

material of the barrel nuts is H–11 steel. 

Therefore, if operators have chosen to 

do the internal and external inspections 

along with the torque check specified in 

paragraph (g)(1) of this AD, and have 

not chosen to do the magnetic check 

specified in paragraph (g)(2) of this AD, 

then they have not determined the 

material of the barrel nuts. For airplanes 

on which the material of the barrel nuts 

has not been determined, the 

requirement is to replace all barrel nuts, 

as required by paragraph (g)(1)(ii)(B) of 

this AD. 

Operators choosing to do the magnetic 

check specified in paragraph (g)(2) of 

this AD would have determined the 

material of the barrel nuts, and may 

replace only H–11 steel barrel nuts, as 

required by paragraph (g)(2)(i)(B)(2) of 

this AD. 

Operators are not permitted to mix 

actions from paragraphs (g)(1) and (g)(2) 

of this AD. Operators may, however, 

submit requests for approval of an 

alternative method of compliance 

(AMOC) to the requirements of 

paragraph (g) of this AD along with 

justification of an equivalent level of 

safety. We have not changed this AD 

regarding this issue. 

Request For Clarification of 

Compliance Time 

UPS requested that we provide an 

exception to the initial inspection 

thresholds of the ‘‘last Torque Check 

Inspection’’ specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 767–53A0261, dated August 12, 

2014. The specified compliance time is 

the later of 24 months after issuance of 

the service information or 36 months 

after the last torque check inspection 

specified in Task 53–734–00, ‘‘Internal, 

Special Detailed, Vertical Stabilizer 

Attach Bolt, of Section 2, ‘‘Structural 

Maintenance Requirements,’’ of the 

Boeing Model 767 Maintenance 

Planning Document. The commenter 

understands that the most recent 

accomplishment of Task 53–734–00 

must be done prior to the effective date 

of this AD. The commenter added that 

if the initial inspection required by 

paragraph (g)(1) or (g)(2) of the proposed 

AD (80 FR 19248, April 10, 2015) is 


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done from the most recent 

accomplishment of Task 53–734–00 and 

that accomplishment occurs after the 

effective date of this AD, the time limits 

given in paragraphs (g)(1)(ii)(B) and 

(g)(2)(i)(B)(2) of this proposed AD may 

be exceeded (i.e., will have already 

passed). 

We agree with the commenter’s 

request and rationale regarding 

providing an exception to the specified 

initial inspection threshold. We have 

redesignated paragraph (h) of the 

proposed AD (80 FR 19248, April 10, 

2015) as paragraph (i)(1) of this AD and 

added new paragraph (i)(2) to this AD 

to provide a compliance time exception 

to address the issue described by the 

commenter. If the most recent 

accomplishment of Task 53–734–00 

occurs after the effective date of this AD, 

then operators still have to comply with 

the requirements of paragraph (g)(1) or 

(g)(2) of this AD. 

Request For Clarification of Effect of 

Winglets on Accomplishment of the 

Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/59027F43B9A7486E

86257B1D006591EE) does not affect the 

actions specified in the NPRM (80 FR 

19248, April 10, 2015). 

We agree with the commenter’s 

statement. We have redesignated 

paragraph (c) of the proposed AD (80 FR 

19248, April 10, 2015) as paragraph 

(c)(1) of this AD, and added new 

paragraph (c)(2) to this AD to state that 

installation of STC ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/59027F43B9A

7486E86257B1D006591EE) does not 

affect the ability to accomplish the 

actions required by this AD. Therefore, 

for airplanes on which STC ST01920SE 

(http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgstc.nsf/0/59027

F43B9A7486E86257B1D006591EE) is 

installed, a ‘‘change in product’’ AMOC 

approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

19248, April 10, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 19248, 

April 10, 2015). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Boeing has issued Alert Service 

Bulletin 767–53A0261, dated August 12, 

2014. The service information describes 

procedures for repetitive internal and 

external detailed inspections of the 

barrel nut holes and sealant for cracked/ 

damaged sealant, corrosion, or a 

cracked/broken barrel nut, and 

replacement of the barrel nut with a 

new Inconel barrel nut if necessary. The 

service information also describes 

procedures for repetitive torque checks 

on each affected vertical fin attachment 

bolt, or, alternatively, a magnetic check 

to identify H–11 steel barrel nuts, and 

replacement with a new Inconel barrel 

nut if necessary. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 38 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on 

U.S. operators 

Option 1: Detailed inspections 

and torque check.

4 work-hours × $85 per hour 

= $340 per inspection cycle.

(1) Up to $482,661 per inspection 

cycle.

Up to $18,341,118. 

Option 2: Magnetic check ...... 4 work-hours × $85 per hour 

= $340.

$0 $340 ....................................... $12,920. 

1For the torque check, operators may choose to rent a special tool, with rental costs up to $482,321. 

We estimate that replacing any barrel 

nut would take 1 work-hour, at an 

average labor rate of $85 per work-hour. 

We have received no definitive data that 

would enable us to provide cost 

estimates for the cost of replacement 

parts. We have no way of determining 

the number of aircraft that might need 

these replacements. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all available costs in our 

cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 


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Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Rules and Regulations 81741 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–26–07 The Boeing Company: 

Amendment 39–18355; Docket No. 

FAA–2015–0683; Directorate Identifier 

2014–NM–196–AD. 

(a) Effective Date 

This AD is effective February 4, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 767–200, –300, –300F series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

767–53A0261, dated August 12, 2014. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

59027F43B9A7486E86257B1D006591EE) 

does not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST01920SE (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

59027F43B9A7486E86257B1D006591EE) is 

installed, a ‘‘change in product’’ alternative 

method of compliance (AMOC) approval 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a finding that 

certain barrel nuts installed at the vertical fin 

may be subject to stress corrosion and 

cracking. We are issuing this AD to detect 

and correct corroded and loose barrel nuts 

that attach the vertical fin to body section 48; 

this condition could result in reduced 

structural integrity of the vertical fin 

attachment joint, loss of the vertical fin, and 

consequent loss of controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

For airplanes identified in Boeing Alert 

Service Bulletin 767–53A0261, dated August 

12, 2014: Do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0261, dated August 12, 2014. Signs 

of corrosion include, but are not limited to, 

sealant cracks, sealant bulging, powder 

residue, and cracked barrel nuts. 

(1) At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 767–53A0261, dated 

August 12, 2014, except as provided by 

paragraph (i) of this AD: Do internal and 

external detailed inspections of the barrel 

nuts and sealant for signs of corrosion, and 

do a torque check of the vertical stabilizer 

attachment bolts for loose barrel nuts. 

(i) If corrosion or any loose barrel nut is 

found at any attachment point location, 

before further flight, replace the barrel nut 

with a new Inconel barrel nut. 

(ii) If no corrosion or loose barrel nut is 

found at any attachment point location, do 

the actions specified in paragraphs 

(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD. 

(A) Repeat the inspections and torque 

check thereafter at intervals not to exceed 18 

months until the replacement specified in 

paragraph (g)(1)(ii)(B) of this AD is done at 

that attachment point location. 

(B) Within 36 months after the effective 

date of this AD, replace all barrel nuts with 

new Inconel barrel nuts. 

(2) At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 767–53A0261, dated 

August 12, 2014, except as provided by 

paragraph (i) of this AD: Do a magnetic check 

to identify H–11 steel barrel nuts. 

(i) If any H–11 steel barrel nut is found at 

any attachment point location, before further 

flight, do an internal and external detailed 

inspection of the barrel nut holes and sealant 

for signs of corrosion, and do a torque check 

of the vertical stabilizer attachment bolts for 

loose barrel nuts. 

(A) If corrosion or any loose barrel nut is 

found, before further flight, replace the barrel 

nut with a new Inconel barrel nut. 

(B) If no corrosion or loose barrel nut is 

found, do the actions specified in paragraphs 

(g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this AD. 

(1) Repeat the inspections and torque 

check thereafter at intervals not to exceed 18 

months until the replacement specified in 

paragraph (g)(2)(i)(B)(2) of this AD is done at 

that attachment point location. 

(2) Within 36 months after the effective 

date of this AD, replace all H–11 steel barrel 

nuts with new Inconel barrel nuts. 

(ii) If no H–11 steel barrel nut is found at 

all attachment point locations, no further 

work is required by this paragraph. 

(h) Terminating Action for Repetitive 

Inspections and Replacement 

(1) Replacing a barrel nut at an attachment 

point location with a new Inconel barrel nut, 

in accordance with Part 5 of Boeing Alert 

Service Bulletin 767–53A0261, dated August 

12, 2014, terminates the inspections and 

replacement required by paragraph (g) of this 

AD for that attachment point location only. 

(2) If no H–11 steel barrel nut is found 

installed at an attachment point location, the 

repetitive inspections and replacement 

required by paragraph (g) of this AD are 

terminated for that attachment location only. 

(i) Exception to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

767–53A0261, dated August 12, 2014, 

specifies a compliance time ‘‘after the 

Original Issue date of this Service Bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Alert Service Bulletin 

767–53A0261, dated August 12, 2014, 

specifies a compliance time after the ‘‘last 

Torque Check Inspection’’ in accordance 

with Task 53–734–00, ‘‘Internal, Special 

Detailed, Vertical Stabilizer Attach Bolt, of 

Section 2, Structural Maintenance 

Requirements,’’ of the Boeing Model 767 

Maintenance Planning Document, that 

compliance time only applies if the most 

recent accomplishment of Task 53–734–00 

occurred on or before the effective date of 

this AD. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an H–11 steel barrel nut 

on the vertical stabilizer of any airplane. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 


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ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(4)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(l) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6447; fax: 425–917–6590; 

email: wayne.lockett@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 767– 

53A0261, dated August 12, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

December 9, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32596 Filed 12–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1480; Directorate 

Identifier 2014–SW–071–AD; Amendment 

39–18352; AD 2015–26–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2002–13– 

11 for Eurocopter France (now Airbus 

Helicopters) Model EC120B helicopters. 

AD 2002–13–11 required installing front 

and side covers on the cabin floor to 

protect the yaw control at both the pilot 

and co-pilot stations. Since we issued 

AD 2002–13–11, we have determined 

that the required actions should apply 

only to the cabin’s right-hand pilot 

station. This AD retains the 

requirements of AD 2002–13–11 but for 

only the pilot station. These actions are 

intended to prevent an object from 

sliding between the canopy and the 

cabin floor, loss of yaw control, and 

subsequent loss of helicopter control. 

DATES: This AD is effective February 4, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 4, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1480 or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the Direction Generale 

de l’Aviation Civile (DGAC) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy, Fort Worth, TX 76177; telephone 

(817) 222–5110; email robert.grant@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2002–13–11, 

Amendment 39–12799 (67 FR 45295, 

July 9, 2002) and add a new AD. AD 

2002–13–11 applied to Airbus Model 

EC120B helicopters, serial numbers 

1001 through 1278, and required 

installing front and side covers to 

protect the yaw control at the pilot and 

co-pilot flight control stations. AD 

2002–13–11 was prompted by AD No. 

2001–386–007(A), dated September 5, 

2001, issued by the DGAC, the 

airworthiness authority for France, to 

correct an unsafe condition for the 

Model EC120B helicopter. The DGAC 

advises of a yaw-control jamming 

caused by an object that slid between 

the canopy and the cabin floor. 

After we issued AD 2002–13–11 (67 

FR 45295, July 9, 2002), we determined 

that the front and side protections are 

required only at the pilot station. The 

NPRM published in the Federal 

Register on May 14, 2015 (80 FR 27605), 

and proposed to supersede AD 2002– 

13–11 to require installing the front and 

side covers only at the pilot station. It 

also reflected that Eurocopter France 

had changed its name to Airbus 

Helicopters. 

Since we issued the NPRM, we 

discovered it contains a typographical 

error in the date of the service 

information. Also, the FAA Southwest 

Regional Office has relocated and a 

group email address has been 

established for requesting an FAA 

Alternate Method of Compliance for a 

helicopter of foreign design. We have 


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